EP3417963A1 - Method for additively manufacturing components - Google Patents
Method for additively manufacturing components Download PDFInfo
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- EP3417963A1 EP3417963A1 EP18179508.9A EP18179508A EP3417963A1 EP 3417963 A1 EP3417963 A1 EP 3417963A1 EP 18179508 A EP18179508 A EP 18179508A EP 3417963 A1 EP3417963 A1 EP 3417963A1
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- layer
- digital
- laser
- power
- component
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 17
- 239000000463 material Substances 0.000 claims abstract description 30
- 239000012254 powdered material Substances 0.000 claims abstract description 20
- 238000005245 sintering Methods 0.000 claims abstract description 17
- 238000000151 deposition Methods 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims description 14
- 238000005056 compaction Methods 0.000 claims description 12
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 8
- 239000000654 additive Substances 0.000 description 6
- 230000000996 additive effect Effects 0.000 description 6
- 239000000155 melt Substances 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000956 alloy Substances 0.000 description 4
- 229910052759 nickel Inorganic materials 0.000 description 4
- 238000013021 overheating Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000011960 computer-aided design Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007499 fusion processing Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/50—Working by transmitting the laser beam through or within the workpiece
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y30/00—Apparatus for additive manufacturing; Details thereof or accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y50/00—Data acquisition or data processing for additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y50/00—Data acquisition or data processing for additive manufacturing
- B33Y50/02—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
- B22F12/40—Radiation means
- B22F12/41—Radiation means characterised by the type, e.g. laser or electron beam
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Definitions
- This disclosure relates to a method of additively manufacturing components, and more particularly, to additively manufacturing components with high fatigue and creep resistance strength requirements.
- Certain components of gas turbine engines are operating at high temperatures and pressures and require high fatigue and creep resistance. To a large extent the microstructure of the material from which the component is formed controls the characteristics of the component. Often, however, there are process constraints and variables that may adversely influence the microstructure-properties relationship, especially in multi-phase, highly alloyed materials.
- a method of making a component according to an example of the present disclosure includes providing a digital model of a component to a software program, the software program operable to slice the digital model into digital layers and raster each digital layer into digital segments, the digital segments delineated by digital raster lines.
- the method further includes depositing a first layer of powdered material onto a platform, compacting the first layer of powered material into a first compacted layer, sintering the first compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at a first power and a first scan speed, and sintering the first compacted layer along a perimeter of the first compacted layer using the laser to form a first unitary layer, wherein the laser operates at a second power and a second scan speed, wherein the ratio of the first power to the second power is less than about 3.
- the first power is between about 200 and 230 W.
- the second power is between about 75 and 105 W.
- the first layer of powdered material has a first thickness after the depositing step.
- the compacting step compacts the first layer of powdered material to a second thickness that is by between about 40% and 60% of the first thickness.
- the second thickness is between about 20 and 40 ⁇ m (0.79 and 1.57 mil).
- the compaction step results in a packed density of the first layer of powdered material of between about 4 and 6 g/cc.
- a distance between the raster lines is between about 30 ⁇ m and 100 ⁇ m (1.18 and 3.94 mils).
- the laser has a beam, and a center point of the beam is offset from an edge of the first unitary layer during the second sintering step such that the beam does not overhang the edge of the first unitary layer.
- the offset includes an outline offset of between about -150 and +150 ⁇ m (-5.91 to +5.91 mils) and a Heart offset of between about -150 and +150 ⁇ m (-5.91 to +5.91 mils).
- a controller is operable to receive signals from the software program and direct the laser during the first and second sintering steps.
- a further embodiment of the any of the foregoing embodiments includes heat treating the first unitary layer and second unitary layer.
- the heat treatment is performed in a hot isostatic press.
- the first unitary layer has an average grain size of between about 40 and 60 ⁇ m (1.57 and 2.36 mils) after the heat treatment.
- the first unitary layer has generally equiaxed grain shapes.
- the first unitary layer has an average density of greater than about 99% after the heat treatment.
- a further embodiment of the any of the foregoing embodiments includes depositing a second layer of powdered material onto the first unitary layer, compacting the second layer of powered material into a second compacted layer, sintering the second compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at the first power and the first scan speed, and sintering the second compacted layer along a perimeter of the second compacted layer using the laser to form a second unitary layer, wherein the laser operates at the second power and the second scan speed.
- the second layer of powdered material has a first t thickness after the depositing step.
- the compacting step compacts the second layer of powdered material to a second thickness, and the second thickness is between about 20 and 40 ⁇ m (0.79 and 1.57 mil).
- the thickness of the second compacted layer is between about 40 and 60% of the thickness of the first compacted layer.
- the laser has a beam, and a center point of the beam is offset from an edge of the second unitary layer during the fourth sintering step such that the beam does not overhang the edge of the second unitary layer.
- the material is a powered nickel alloy, and wherein the component is a heat exchanger is operable at temperatures greater than 1600°F (871°C).
- An apparatus for making a component includes a controller operable to receive signals from a software program.
- the software program is operable to slice a digital model of a component into digital layers and raster each digital layer into digital segments.
- the digital segments are delineated by digital raster lines, a material source operable to provide material to a platform, a compactor operable to compact the material, and a laser operable to sinter the material.
- the laser is movable by the controller to sinter the material along the raster lines at a first power and a first speed and along a perimeter of the component at a second power and a second scan speed.
- the ratio of the first power to the second power is less than about 3.
- Figures 1A-B show a schematic view of an example gas turbine engine component 20.
- the component 20 is a heat exchanger. More particularly, the component 20 is a heat exchanger operable at temperatures greater than 1600° F (871° C) without failure of the heat exchanger. As will be appreciated, this disclosure is not limited to heat exchangers and the examples herein apply to other components.
- the component 20 is formed from a nickel-based alloy with composition shown in Table 1 below. More particularly, the nickel-based alloy is Haynes® 282® (Haynes International) powder. Table 1 Weight % Chromium 20 Cobalt 10 Molybdenum 8.5 Titanium 2.1 Aluminum 1.5 Iron 1.5 max Manganese 0.3 max Silicon 0.15 max Carbon 0.06 Boron 0.005 Nickel Balance
- the component 20 is shown with an example geometry, the component 20 can have any shape, including areas of non-uniform thicknesses.
- Heat exchangers in particular often include thick areas (such as manifolds) and thinner areas (such as fins), which may be solid or hollow, or include internal features such as cooling passages.
- the component 20 is formed by an additive manufacturing process, such as a powder-bed fusion process. More particularly, the component 20 is formed by a laser selective melting process. The component 20 is subjected to a heat treatment after being additively manufactured, which will be discussed in more detail below.
- an additive manufacturing process such as a powder-bed fusion process. More particularly, the component 20 is formed by a laser selective melting process.
- the component 20 is subjected to a heat treatment after being additively manufactured, which will be discussed in more detail below.
- FIG. 2 shows an example additive manufacturing system 22.
- the system 22 includes a platform 24, a laser 26, a powder reservoir 28, a compaction-style recoater 30 (such as a rolling recoater system), and a controller 31 operable to direct movement of the laser beam 26.
- the controller 31 includes necessary software and/or hardware to perform the functions disclosed herein.
- material such as powdered nickel-based alloy, discussed above
- the controller 31 receives signals from a software program to direct the laser 26 to selectively melt portions of the compacted material according to a sliced file derived from a CAD model's component geometry in the software program to form the component 20.
- FIG 3A schematically shows a method 100 of additively manufacturing the component 20 with the additive manufacturing system 22.
- a digital model such as a computer-aided design file, of the desired shape of the component 20 is provided to a software program for rastering (step 102).
- the software program creates digital "slices" or layers of the component shape in the z-direction.
- layers 32 are shown on the physical component 20 corresponding to the digital model.
- Each digital layer has a thickness T, which ranges between about 10 and 80 ⁇ m (0.39 to 3.15 mils) on corresponding component 20.
- the software program also divides the digital layer into segments in the x-y plane delineated by raster lines.
- Segments 34 and raster lines 36 are shown in Figure 1B on the physical component 20 corresponding to the digital model.
- a distance H between raster lines known as a hatch distance is shown on the physical component 20 corresponding to the digital model in Figure 1B .
- the distance H is between about 30 ⁇ m and 100 ⁇ m (1.18 and 3.94 mils). In a particular example, the distance H is between about 40 ⁇ m and 60 ⁇ m (1.57 and 2.36 mils).
- rastering also includes segmenting each layer 32 into "tiles" which can have any shape (square, hexagonal, etc.). This strategy is generally used for larger parts to prevent component warping due to the high density of residual stresses and thermal lensing during the additive manufacturing process.
- step 104 the component is formed or built by additive manufacturing.
- the building process 200 is shown in more detail in Figure 3B and discussed below.
- step 106 a heat treatment is performed, which will also be discussed below.
- a first layer 32A of powdered material such as the nickel-based alloy described above, is deposited onto the platform 24 from the material source 28 ( Figure 2 ).
- the first layer 32A is compacted with the compaction-style recoater 30.
- the compaction step 204 compacts the first layer 32A by between 0 and 50% of the thickness T1 to form a layer 32A having thickness T1'.
- the compaction step 204 compacts the first layer 32 by between about 20 and 40%.
- the compaction step results in a packed density of the powdered material of between about 4 and 6 g/cc.
- the packed density is between about 4.8 and 5.3 g/cc.
- This first layer 32A also known as the "initial down," has a thickness T1' of between about 40 and 100 ⁇ m (1.57 and 3.94 mils) after compaction in step 204.
- the thickness T1' is between about 50 and 70 ⁇ m (1.97 and 2.76 mil) after compaction in step 204.
- the software program directs the laser 26 along the digital raster lines 36 to sinter (or melt) the powdered material into a unitary solid layer 32A, shown in Figure 4 .
- the laser 26 is directed along the all the raster lines 36 of a single tile before moving on to another tile and repeating the process.
- the laser 26 is directed along various paths, depending on the scan strategy. Scan strategies can be comprised of one or more scan styles to fill in the bulk of the layer 32A. The example scan strategy described herein is known as "heart fill.”
- the software program directs the laser 26 via the controller 31.
- the software program describes the laser 26 inputs that control the energy provided to a specific quantifiable area, which is the area of the projection of a laser beam 126 onto the component 20 (shown in Figure 5 ). These inputs include the power output of the laser 26, and the speed of the laser 26 traversing over the build plan (or the "scan speed"). The scan speed and power are dependent on the machine capability.
- the laser 26 operates at a range between 0 and 1000 W over the area of the projection of a laser beam 126 onto the component 20. In a particular example, the laser 26 operates at power range of between about 200 and 230 W area of the projection of the laser beam 126 onto the component 20.
- the laser 26 operates at a scan speed of between about 2000 and 2500 mm/second (78.74 and 98.43 in/second). In a particular example, the laser 26 operates at a scan speed of between about 2250 and 2350 mm/second (88.58 and 92.52 in/second).
- the focused laser beam 126 diameter can range from 50 to 80 microns, with a center point C. If the hatch distance H (discussed above) is too large, the component 20 will have voids in between the raster lines 36 because there will be areas in between the raster lines 36 that are not sintered properly. If it is too small, the sintering step can take multiple passes over the same material and cause overheating and/or distortion.
- the hatch distance H is thus related to the size of the laser beam (discussed in more detail below) and is selected to minimize both voids and overheating/distortion in the final component 20. Generally hatch distance H is selected to provide a small amount of overlap between successive passes of the laser 26. Step 206 is sometimes known as a "hex scan.”
- the laser 26 is directed by the software program via the controller 31 along the perimeter of the layer 32A to in a subsequent scan strategy, known as a "contour scan," to solidify the perimeter of the layer 32A.
- the laser 26 operates at a power range between 0 and 1000 W over the area of the projection of the laser beam 126 onto the component 20.
- the laser 26 operates at power range between about 75 to 105 W over the area of the projection of a laser beam 126 onto the component 20.
- the laser 26 operates at a scan speed of between about 2000 and 2500 mm/second (78.74 and 98.43 in/second).
- the laser 26 operates at a scan speed of between about 1425 and 1575 mm/second (56.10 and 62.00 in/second).
- the ratio of the laser 26 power density in step 206 to the ratio of the power density in step 208 is less than about 3. More particularly, the ratio is between about 2.67 and 2.19.
- the laser 26 produces a beam 126 with a center point C and a radius R.
- the radius R is between about 25 and 50 ⁇ m (0.98 and 1.97 mils).
- the beam 126 corresponds to a "melt pool" of material on the component 20.
- the melt pool has a radius of between about 30 and 40 ⁇ m (1.18 and 1.57 mils).
- the center point C of the laser beam 126 is offset from a nominal edge 132 of component 20. Like the hatch distance H, an offset is selected to prevent overheating and/or distortion of material sintered during step 206 above, while also providing some small amount of overlap of sintered material to minimize voids in the perimeter of the layer 32A. In one example, the beam 126 is also offset so as not to overhang the edge 132. This maintains the desired shape of the component 20. In one example, the center point C is offset during step 206 to provide a linear offset of between about -150 and +150 ⁇ m (-5.91 to +5.91 mils). In a particular example, the linear offset is between about -80 and -100 ⁇ m (-3.15 and -3.94 mil). In another example, the linear offset is related to the size of a melt pool created by the beam 126. For instance, the linear offset is between about 40% and 60% of a diameter of the melt pool.
- the center point C is offset during the contour scanning of step 208 in two dimensions.
- the "outline offset" shifts the center point C with respect to the nominal edge 132.
- a negative outline offset shifts the outer contour of the component 20 towards a center point of layer 32A and a positive offset shifts the outer contour of the component 20 away from a center point of layer 32A.
- the outline offset is related to the size of the melt pool created by the beam 126.
- the outline offset is between about 40% and 60% of a diameter of the melt pool.
- the outline offset is between about -150 and +150 ⁇ m (-5.91 to +5.91 mils) from the nominal edge 132 of component 20.
- the outline offset is between about -50 and -70 ⁇ m (-1.97 and -2.76 mil).
- the outline offset is less than the liner offset discussed above.
- the center point C of the laser beam 126 also has a "heart offset" which is related to the mathematical edge of the contour of component 20.
- the heart offset value refers to the laser beam position 126 to compensate for the edge of the beam 126 at the edge 132 of the component 20, which is as close as possible to the nominal dimension of the component 20 as determined by the software program discussed above.
- the heart offset is between about 150 and +150 ⁇ m. In a particular example, the heart offset is between about -80 and -100 ⁇ m (-3.15 and -3.94 mil).
- step 210 the platform 24 is lowered and a second layer 32B of material is deposited onto the first layer 32A from the material source 28.
- the second layer 40 is compacted in step 212 by between 0 and 50% of the thickness T2 to form a layer 40 having thickness T2', as shown in Figure 4 .
- the compaction step 212 compacts the second layer 40 by between about 30 and 40%.
- the thickness T2' is less than the initial down thickness T1'.
- the thickness T2' of the second layer 32B is between about 20 and 40 ⁇ m (0.79 and 1.57 mil).
- the thickness T2' is between about 25 and 35 ⁇ m (0.98 and 1.38 mil).
- the thickness T2' is between about 40 and 60% of the thickness T1'.
- step 214 the software program directs the laser along the digital raster lines to sinter (or melt) the powdered material into a unitary solid layer 32B, shown in Figure 4 , as in step 206.
- step 216 the second layer 32B is contour scanned as in step 208. Steps 210, 212, and 214, and 216 are then repeated until the component 20 has the desired shape.
- Table 2 below shows the relationship between laser power (P), scan speed (V), layer 32A, 32B thickness (T), compaction percentage of the powdered material, and hatch distance (H).Each column shows the effect on the other variables where one variable is increased. For instance, looking to the first column, an increased P corresponds to increased V, T, and H and decreased compaction percentage.
- Table 2 Increased P Increased V Increased T Increased Compaction % Increased H P + + - + V + - + - T + - + - Compaction - + + + + H + - - + +
- a heat treatment is performed on the component 20 after it is formed.
- the heat treatment further solidifies the component 20.
- heat treatment is performed in a hot isostatic press ("HIP") and can include solutionizing heat treatment.
- HIP hot isostatic press
- the heat treatment can be performed in a single cycle, minimizing the time the component 20 is held at a high temperature, which in turn translates to finer grain size in the component 20 microstructure and improved fatigue properties. Because the heat treatment can be performed in a single cycle, manufacturing time and cost is reduced.
- the process parameters described above (including the laser 26 power and scan speed, the layer 32A, 32B thickness T1' and T2', the hatch distance H, and the outline and heart offsets) produce a component 20 with improved fatigue and creep resistance.
- Fatigue and creep resistance are related to the microstructure of the component 20.
- the component 20 formed as discussed above has high density, greater than approximately 99, and in one example, approximately 99.8%, and minimized porosity which contributes to its improved fatigue and creep resistance.
- the component 20 has a grain morphology with generally uniform grain size, between about 40 ⁇ m and 60 ⁇ m average grain size between 40 and 60 ⁇ m (1.57 and 2.36 mils), and generally close to equiaxed grain shapes, which also contributes to its improved homogeneity and Young modulus. Furthermore, the microstructure of component 20 can be obtained in both thick and thin areas of component 20 with the method described above. That is, minimal or no process changes are needed to obtain high fatigue and creep resistance over the entire component 20, irrespective of its shape, meaning manufacturing costs and time are lowered.
Abstract
Description
- This disclosure relates to a method of additively manufacturing components, and more particularly, to additively manufacturing components with high fatigue and creep resistance strength requirements.
- Certain components of gas turbine engines are operating at high temperatures and pressures and require high fatigue and creep resistance. To a large extent the microstructure of the material from which the component is formed controls the characteristics of the component. Often, however, there are process constraints and variables that may adversely influence the microstructure-properties relationship, especially in multi-phase, highly alloyed materials.
- A method of making a component according to an example of the present disclosure includes providing a digital model of a component to a software program, the software program operable to slice the digital model into digital layers and raster each digital layer into digital segments, the digital segments delineated by digital raster lines. The method further includes depositing a first layer of powdered material onto a platform, compacting the first layer of powered material into a first compacted layer, sintering the first compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at a first power and a first scan speed, and sintering the first compacted layer along a perimeter of the first compacted layer using the laser to form a first unitary layer, wherein the laser operates at a second power and a second scan speed, wherein the ratio of the first power to the second power is less than about 3.
- In a further embodiment of the foregoing embodiment, the first power is between about 200 and 230 W.
- In a further embodiment of any of the foregoing embodiments, the second power is between about 75 and 105 W.
- In a further embodiment of any of the foregoing embodiments, the first layer of powdered material has a first thickness after the depositing step. The compacting step compacts the first layer of powdered material to a second thickness that is by between about 40% and 60% of the first thickness.
- In a further embodiment of any of the foregoing embodiments, the second thickness is between about 20 and 40 µm (0.79 and 1.57 mil).
- In a further embodiment of any of the foregoing embodiments, the compaction step results in a packed density of the first layer of powdered material of between about 4 and 6 g/cc.
- In a further embodiment of any of the foregoing embodiments, a distance between the raster lines is between about 30 µm and 100 µm (1.18 and 3.94 mils).
- In a further embodiment of any of the foregoing embodiments, the laser has a beam, and a center point of the beam is offset from an edge of the first unitary layer during the second sintering step such that the beam does not overhang the edge of the first unitary layer.
- In a further embodiment of any of the foregoing embodiments, the offset includes an outline offset of between about -150 and +150 µm (-5.91 to +5.91 mils) and a Heart offset of between about -150 and +150 µm (-5.91 to +5.91 mils).
- In a further embodiment of any of the foregoing embodiments, a controller is operable to receive signals from the software program and direct the laser during the first and second sintering steps.
- A further embodiment of the any of the foregoing embodiments includes heat treating the first unitary layer and second unitary layer. The heat treatment is performed in a hot isostatic press.
- In a further embodiment of any of the foregoing embodiments, the first unitary layer has an average grain size of between about 40 and 60 µm (1.57 and 2.36 mils) after the heat treatment.
- In a further embodiment of any of the foregoing embodiments, the first unitary layer has generally equiaxed grain shapes.
- In a further embodiment of any of the foregoing embodiments, the first unitary layer has an average density of greater than about 99% after the heat treatment.
- A further embodiment of the any of the foregoing embodiments includes depositing a second layer of powdered material onto the first unitary layer, compacting the second layer of powered material into a second compacted layer, sintering the second compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at the first power and the first scan speed, and sintering the second compacted layer along a perimeter of the second compacted layer using the laser to form a second unitary layer, wherein the laser operates at the second power and the second scan speed.
- In a further embodiment of any of the foregoing embodiments, the second layer of powdered material has a first t thickness after the depositing step. The compacting step compacts the second layer of powdered material to a second thickness, and the second thickness is between about 20 and 40 µm (0.79 and 1.57 mil).
- In a further embodiment of any of the foregoing embodiments, the thickness of the second compacted layer is between about 40 and 60% of the thickness of the first compacted layer.
- In a further embodiment of any of the foregoing embodiments, the laser has a beam, and a center point of the beam is offset from an edge of the second unitary layer during the fourth sintering step such that the beam does not overhang the edge of the second unitary layer.
- In a further embodiment of any of the foregoing embodiments, the material is a powered nickel alloy, and wherein the component is a heat exchanger is operable at temperatures greater than 1600°F (871°C).
- An apparatus for making a component according to an example of the present disclosure includes a controller operable to receive signals from a software program. The software program is operable to slice a digital model of a component into digital layers and raster each digital layer into digital segments. The digital segments are delineated by digital raster lines, a material source operable to provide material to a platform, a compactor operable to compact the material, and a laser operable to sinter the material. The laser is movable by the controller to sinter the material along the raster lines at a first power and a first speed and along a perimeter of the component at a second power and a second scan speed. The ratio of the first power to the second power is less than about 3.
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Figure 1A schematically illustrates an example gas turbine engine component. - Figure IB schematically illustrates a layer of the example gas turbine engine component, a top-down view.
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Figure 2 schematically illustrates an additive manufacturing system. -
Figure 3A schematically illustrates a method of additively manufacturing the component. -
Figure 3B schematically illustrates a building process of the method of additively manufacturing the component. -
Figure 4 schematically illustrates a component being additively manufactured on a platform. -
Figure 5 schematically illustrates a top-down view ofFigure 4 . -
Figures 1A-B show a schematic view of an example gasturbine engine component 20. In the example ofFigures 1A-B , thecomponent 20 is a heat exchanger. More particularly, thecomponent 20 is a heat exchanger operable at temperatures greater than 1600° F (871° C) without failure of the heat exchanger. As will be appreciated, this disclosure is not limited to heat exchangers and the examples herein apply to other components. Thecomponent 20 is formed from a nickel-based alloy with composition shown in Table 1 below. More particularly, the nickel-based alloy is Haynes® 282® (Haynes International) powder.Table 1 Weight % Chromium 20 Cobalt 10 Molybdenum 8.5 Titanium 2.1 Aluminum 1.5 Iron 1.5 max Manganese 0.3 max Silicon 0.15 max Carbon 0.06 Boron 0.005 Nickel Balance - Though the
component 20 is shown with an example geometry, thecomponent 20 can have any shape, including areas of non-uniform thicknesses. Heat exchangers in particular often include thick areas (such as manifolds) and thinner areas (such as fins), which may be solid or hollow, or include internal features such as cooling passages. - The
component 20 is formed by an additive manufacturing process, such as a powder-bed fusion process. More particularly, thecomponent 20 is formed by a laser selective melting process. Thecomponent 20 is subjected to a heat treatment after being additively manufactured, which will be discussed in more detail below. -
Figure 2 shows an exampleadditive manufacturing system 22. Thesystem 22 includes aplatform 24, alaser 26, apowder reservoir 28, a compaction-style recoater 30 (such as a rolling recoater system), and acontroller 31 operable to direct movement of thelaser beam 26. Thecontroller 31 includes necessary software and/or hardware to perform the functions disclosed herein. In general, material (such as powdered nickel-based alloy, discussed above) from thematerial source 28 is deposited onto theplatform 24. The material is then compacted with the compaction-style recoater 30. Thecontroller 31 receives signals from a software program to direct thelaser 26 to selectively melt portions of the compacted material according to a sliced file derived from a CAD model's component geometry in the software program to form thecomponent 20. -
Figure 3A schematically shows amethod 100 of additively manufacturing thecomponent 20 with theadditive manufacturing system 22. A digital model, such as a computer-aided design file, of the desired shape of thecomponent 20 is provided to a software program for rastering (step 102). During rastering, the software program creates digital "slices" or layers of the component shape in the z-direction. InFigures 1A-B ,layers 32 are shown on thephysical component 20 corresponding to the digital model. Each digital layer has a thickness T, which ranges between about 10 and 80 µm (0.39 to 3.15 mils) on correspondingcomponent 20. The software program also divides the digital layer into segments in the x-y plane delineated by raster lines.Segments 34 and raster lines 36 are shown inFigure 1B on thephysical component 20 corresponding to the digital model. A distance H between raster lines known as a hatch distance, and is shown on thephysical component 20 corresponding to the digital model inFigure 1B . In one example, the distance H is between about 30 µm and 100 µm (1.18 and 3.94 mils). In a particular example, the distance H is between about 40 µm and 60 µm (1.57 and 2.36 mils). - In a further example, rastering (step 102) also includes segmenting each
layer 32 into "tiles" which can have any shape (square, hexagonal, etc.). This strategy is generally used for larger parts to prevent component warping due to the high density of residual stresses and thermal lensing during the additive manufacturing process. - Referring back to
Figure 3A , instep 104 the component is formed or built by additive manufacturing. Thebuilding process 200 is shown in more detail inFigure 3B and discussed below. Instep 106, a heat treatment is performed, which will also be discussed below. - Referring now to the
building process 200 shown inFigure 3B , instep 202, afirst layer 32A of powdered material, such as the nickel-based alloy described above, is deposited onto theplatform 24 from the material source 28 (Figure 2 ). Instep 204, thefirst layer 32A is compacted with the compaction-style recoater 30. Thecompaction step 204 compacts thefirst layer 32A by between 0 and 50% of the thickness T1 to form alayer 32A having thickness T1'. In a particular example, thecompaction step 204 compacts thefirst layer 32 by between about 20 and 40%. The compaction step results in a packed density of the powdered material of between about 4 and 6 g/cc. More particularly, the packed density is between about 4.8 and 5.3 g/cc. Thisfirst layer 32A, also known as the "initial down," has a thickness T1' of between about 40 and 100 µm (1.57 and 3.94 mils) after compaction instep 204. In one particular example, the thickness T1' is between about 50 and 70 µm (1.97 and 2.76 mil) after compaction instep 204. - In
step 206, the software program directs thelaser 26 along the digital raster lines 36 to sinter (or melt) the powdered material into a unitarysolid layer 32A, shown inFigure 4 . In one example, if thelayer 32A is further rastered into "tiles," thelaser 26 is directed along the all the raster lines 36 of a single tile before moving on to another tile and repeating the process. In other examples, thelaser 26 is directed along various paths, depending on the scan strategy. Scan strategies can be comprised of one or more scan styles to fill in the bulk of thelayer 32A. The example scan strategy described herein is known as "heart fill." The software program directs thelaser 26 via thecontroller 31. The software program describes thelaser 26 inputs that control the energy provided to a specific quantifiable area, which is the area of the projection of alaser beam 126 onto the component 20 (shown inFigure 5 ). These inputs include the power output of thelaser 26, and the speed of thelaser 26 traversing over the build plan (or the "scan speed"). The scan speed and power are dependent on the machine capability. In one example, thelaser 26 operates at a range between 0 and 1000 W over the area of the projection of alaser beam 126 onto thecomponent 20. In a particular example, thelaser 26 operates at power range of between about 200 and 230 W area of the projection of thelaser beam 126 onto thecomponent 20. In one example, thelaser 26 operates at a scan speed of between about 2000 and 2500 mm/second (78.74 and 98.43 in/second). In a particular example, thelaser 26 operates at a scan speed of between about 2250 and 2350 mm/second (88.58 and 92.52 in/second). Thefocused laser beam 126 diameter can range from 50 to 80 microns, with a center point C. If the hatch distance H (discussed above) is too large, thecomponent 20 will have voids in between the raster lines 36 because there will be areas in between the raster lines 36 that are not sintered properly. If it is too small, the sintering step can take multiple passes over the same material and cause overheating and/or distortion. The hatch distance H is thus related to the size of the laser beam (discussed in more detail below) and is selected to minimize both voids and overheating/distortion in thefinal component 20. Generally hatch distance H is selected to provide a small amount of overlap between successive passes of thelaser 26. Step 206 is sometimes known as a "hex scan." - In
step 208, thelaser 26 is directed by the software program via thecontroller 31 along the perimeter of thelayer 32A to in a subsequent scan strategy, known as a "contour scan," to solidify the perimeter of thelayer 32A. In one example, thelaser 26 operates at a power range between 0 and 1000 W over the area of the projection of thelaser beam 126 onto thecomponent 20. In a particular example, thelaser 26 operates at power range between about 75 to 105 W over the area of the projection of alaser beam 126 onto thecomponent 20. In one example, thelaser 26 operates at a scan speed of between about 2000 and 2500 mm/second (78.74 and 98.43 in/second). In a particular example, thelaser 26 operates at a scan speed of between about 1425 and 1575 mm/second (56.10 and 62.00 in/second). - In one example, the ratio of the
laser 26 power density instep 206 to the ratio of the power density instep 208 is less than about 3. More particularly, the ratio is between about 2.67 and 2.19. - Referring to
Figure 5 , thelaser 26 produces abeam 126 with a center point C and a radius R. In some examples, the radius R is between about 25 and 50 µm (0.98 and 1.97 mils). Thebeam 126 corresponds to a "melt pool" of material on thecomponent 20. In some examples, the melt pool has a radius of between about 30 and 40 µm (1.18 and 1.57 mils). - The center point C of the
laser beam 126 is offset from anominal edge 132 ofcomponent 20. Like the hatch distance H, an offset is selected to prevent overheating and/or distortion of material sintered duringstep 206 above, while also providing some small amount of overlap of sintered material to minimize voids in the perimeter of thelayer 32A. In one example, thebeam 126 is also offset so as not to overhang theedge 132. This maintains the desired shape of thecomponent 20. In one example, the center point C is offset duringstep 206 to provide a linear offset of between about -150 and +150 µm (-5.91 to +5.91 mils). In a particular example, the linear offset is between about -80 and -100 µm (-3.15 and -3.94 mil). In another example, the linear offset is related to the size of a melt pool created by thebeam 126. For instance, the linear offset is between about 40% and 60% of a diameter of the melt pool. - In some examples, the center point C is offset during the contour scanning of
step 208 in two dimensions. First, the "outline offset" shifts the center point C with respect to thenominal edge 132. A negative outline offset shifts the outer contour of thecomponent 20 towards a center point oflayer 32A and a positive offset shifts the outer contour of thecomponent 20 away from a center point oflayer 32A. In one example, the outline offset is related to the size of the melt pool created by thebeam 126. For example, the outline offset is between about 40% and 60% of a diameter of the melt pool. In another example, the outline offset is between about -150 and +150 µm (-5.91 to +5.91 mils) from thenominal edge 132 ofcomponent 20. In a particular example, the outline offset is between about -50 and -70 µm (-1.97 and -2.76 mil). - In a further example, the outline offset is less than the liner offset discussed above. The center point C of the
laser beam 126 also has a "heart offset" which is related to the mathematical edge of the contour ofcomponent 20. The heart offset value refers to thelaser beam position 126 to compensate for the edge of thebeam 126 at theedge 132 of thecomponent 20, which is as close as possible to the nominal dimension of thecomponent 20 as determined by the software program discussed above. In one example, the heart offset is between about 150 and +150 µm. In a particular example, the heart offset is between about -80 and -100 µm (-3.15 and -3.94 mil). - In
step 210, theplatform 24 is lowered and asecond layer 32B of material is deposited onto thefirst layer 32A from thematerial source 28. The second layer 40 is compacted instep 212 by between 0 and 50% of the thickness T2 to form a layer 40 having thickness T2', as shown inFigure 4 . In a particular example, thecompaction step 212 compacts the second layer 40 by between about 30 and 40%. In one example, the thickness T2' is less than the initial down thickness T1'. The thickness T2' of thesecond layer 32B is between about 20 and 40 µm (0.79 and 1.57 mil). In a particular example, the thickness T2' is between about 25 and 35 µm (0.98 and 1.38 mil). In another particular example, the thickness T2' is between about 40 and 60% of the thickness T1'. - In
step 214, the software program directs the laser along the digital raster lines to sinter (or melt) the powdered material into a unitarysolid layer 32B, shown inFigure 4 , as instep 206. - In
step 216, thesecond layer 32B is contour scanned as instep 208.Steps component 20 has the desired shape. - Table 2 below shows the relationship between laser power (P), scan speed (V),
layer Table 2 Increased P Increased V Increased T Increased Compaction % Increased H P + + - + V + - + - T + - + - Compaction - + + + H + - - + - Referring back to
Figure 3A , instep 106, a heat treatment is performed on thecomponent 20 after it is formed. The heat treatment further solidifies thecomponent 20. In one example, heat treatment is performed in a hot isostatic press ("HIP") and can include solutionizing heat treatment. The heat treatment can be performed in a single cycle, minimizing the time thecomponent 20 is held at a high temperature, which in turn translates to finer grain size in thecomponent 20 microstructure and improved fatigue properties. Because the heat treatment can be performed in a single cycle, manufacturing time and cost is reduced. - Typically with nickel alloy components, there is a tradeoff between fatigue and creep resistance. The process parameters described above (including the
laser 26 power and scan speed, thelayer component 20 with improved fatigue and creep resistance. Fatigue and creep resistance are related to the microstructure of thecomponent 20. Thecomponent 20 formed as discussed above has high density, greater than approximately 99, and in one example, approximately 99.8%, and minimized porosity which contributes to its improved fatigue and creep resistance. Thecomponent 20 has a grain morphology with generally uniform grain size, between about 40 µm and 60 µm average grain size between 40 and 60 µm (1.57 and 2.36 mils), and generally close to equiaxed grain shapes, which also contributes to its improved homogeneity and Young modulus. Furthermore, the microstructure ofcomponent 20 can be obtained in both thick and thin areas ofcomponent 20 with the method described above. That is, minimal or no process changes are needed to obtain high fatigue and creep resistance over theentire component 20, irrespective of its shape, meaning manufacturing costs and time are lowered. - Furthermore, the foregoing description shall be interpreted as illustrative and not in any limiting sense. A worker of ordinary skill in the art would understand that certain modifications could come within the scope of this disclosure. For these reasons, the following claims should be studied to determine the true scope and content of this disclosure.
Claims (15)
- A method of making a component (20), comprising:providing (102) a digital model of a component to a software program, the software program operable to slice the digital model into digital layers and raster each digital layer into digital segments, the digital segments delineated by digital raster lines;depositing (202) a first layer of powdered material onto a platform;compacting (204) the first layer of powered material into a first compacted layer;sintering the first compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at a first power and a first scan speed; andsintering (206) the first compacted layer along a perimeter of the first compacted layer using the laser to form a first unitary layer, wherein the laser operates at a second power and a second scan speed, wherein the ratio of the first power to the second power is less than about 3.
- The method of claim 1, wherein, the first power is between about 200 and 230 W, and/or
wherein the second power is between about 75 and 105 W. - The method of claim 1 or 2, wherein the first layer of powdered material has a first thickness after the depositing step, and wherein the compacting step compacts the first layer of powdered material to a second thickness that is by between about 40% and 60% of the first thickness, and preferably
wherein the second thickness is between about 20 and 40 µm (0.79 and 1.57 mil). - The method of any preceding claim, wherein the compaction step results in a packed density of the first layer of powdered material of between about 4 and 6 g/cc, and/or
wherein a distance between the raster lines is between about 30 µm and 100 µm (1.18 and 3.94 mils). - The method of any preceding claim, wherein the laser has a beam, and a center point of the beam is offset from an edge of the first unitary layer during the second sintering step such that the beam does not overhang the edge of the first unitary layer, and preferably
wherein the offset includes an outline offset of between about -150 and +150 µm (-5.91 to +5.91 mils) and a Heart offset of between about -150 and +150 µm (-5.91 to +5.91 mils). - The method of any preceding claim, wherein a controller is operable to receive signals from the software program and direct the laser during the first and second sintering steps.
- The method of any preceding claim, further comprising heat treating the first unitary layer and second unitary layer, wherein the heat treatment is performed in a hot isostatic press.
- The method of claim 7, wherein the first unitary layer has an average grain size of between about 40 and 60 µm (1.57 and 2.36 mils) after the heat treatment, and preferably
wherein the first unitary layer has generally equiaxed grain shapes. - The method of claim 7 or 8, wherein the first unitary layer has an average density of greater than about 99% after the heat treatment.
- The method of any preceding claim, further comprising:depositing (210) a second layer of powdered material onto the first unitary layer;compacting (212) the second layer of powered material into a second compacted layer;sintering (214) the second compacted layer along lines corresponding to the digital raster lines using a laser, wherein the laser operates at the first power and the first scan speed; andsintering the second compacted layer along a perimeter of the second compacted layer using the laser to form a second unitary layer, wherein the laser operates at the second power and the second scan speed.
- The method of claim 10, wherein the second layer of powdered material has a first t thickness after the depositing step, and wherein the compacting step compacts the second layer of powdered material to a second thickness, and the second thickness is between about 20 and 40 µm (0.79 and 1.57 mil).
- The method of claim 10 or 11, wherein the thickness of the second compacted layer is between about 40 and 60% of the thickness of the first compacted layer.
- The method of claim 10, 11 or 12, wherein the laser has a beam, and a center point of the beam is offset from an edge of the second unitary layer during the fourth sintering step such that the beam does not overhang the edge of the second unitary layer.
- The method of any preceding claim, wherein the material is a powered nickel alloy, and wherein the component is a heat exchanger is operable at temperatures greater than 1600°F (871°C).
- An apparatus for making a component, comprising:a controller operable to receive signals from a software program, the software program operable to slice a digital model of a component into digital layers and raster each digital layer into digital segments, the digital segments delineated by digital raster lines;a material source operable to provide material to a platform;a compactor operable to compact the material; anda laser operable to sinter the material, the laser movable by the controller to sinter the material along the raster lines at a first power and a first speed and along a perimeter of the component at a second power and a second scan speed, wherein the ratio of the first power to the second power is less than about 3.
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3486005A1 (en) * | 2017-10-17 | 2019-05-22 | Hamilton Sundstrand Corporation | Method for additively manufacturing components |
US10730281B2 (en) | 2017-06-23 | 2020-08-04 | Hamilton Sundstrand Corporation | Method for additively manufacturing components |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3858519A1 (en) | 2020-01-29 | 2021-08-04 | Siemens Aktiengesellschaft | 3d printing method and tool |
US11850800B2 (en) | 2020-12-22 | 2023-12-26 | Hamilton Sundstrand Corporation | Accounting for inducing variables in additive manufacturing |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014074947A2 (en) * | 2012-11-08 | 2014-05-15 | Das, Suman | Systems and methods for additive manufacturing and repair of metal components |
EP2865465A1 (en) * | 2013-09-27 | 2015-04-29 | Alstom Technology Ltd | Method for manufacturing a metallic component by additive laser manufacturing |
WO2016201309A1 (en) * | 2015-06-10 | 2016-12-15 | Ipg Photonics Corporation | Multiple beam additive manufacturing |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100190024A1 (en) * | 2009-01-26 | 2010-07-29 | Netshape Technologies, Inc | Sintered copper-based material having increased grain size and method of making the same |
US8679269B2 (en) * | 2011-05-05 | 2014-03-25 | General Electric Company | Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby |
GB201213940D0 (en) | 2012-08-06 | 2012-09-19 | Materials Solutions | Additive manufacturing |
JP6359640B2 (en) | 2013-04-26 | 2018-07-18 | ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation | Selective laser melting system |
WO2014179679A1 (en) | 2013-05-03 | 2014-11-06 | United Technologies Corporation | Method of eliminating sub-surface porosity |
US9555612B2 (en) | 2014-02-19 | 2017-01-31 | General Electric Company | Treated component and methods of forming a treated component |
US20150367577A1 (en) * | 2014-06-19 | 2015-12-24 | Materialise N.V. | Use of multiple beam spot sizes for obtaining improved performance in optical additive manufacturing techniques |
US10590516B2 (en) * | 2014-06-24 | 2020-03-17 | Commonwealth Scientific And Industrial Research Organisation | Alloy for catalytic membrane reactors |
WO2016013498A1 (en) | 2014-07-23 | 2016-01-28 | 株式会社日立製作所 | Alloy structure and method for manufacturing alloy structure |
EP3025809B1 (en) | 2014-11-28 | 2017-11-08 | Ansaldo Energia IP UK Limited | Method for manufacturing a component using an additive manufacturing process |
US20160348216A1 (en) | 2014-12-16 | 2016-12-01 | Honeywell International Inc. | Nickel-based superalloys and additive manufacturing processes using nickel-based superalloys |
EP3034203A1 (en) | 2014-12-19 | 2016-06-22 | Alstom Technology Ltd | Method for producing a metallic component |
PL3095591T3 (en) | 2015-05-19 | 2020-06-29 | MTU Aero Engines AG | Method and device for detecting at least sections of a contour of a layer of an object obtainable by additive processing |
GB201510220D0 (en) | 2015-06-11 | 2015-07-29 | Renishaw Plc | Additive manufacturing apparatus and method |
US10443495B2 (en) * | 2017-04-14 | 2019-10-15 | Enexor Energy | Combined heat and power system and method of operation |
US11179777B2 (en) * | 2017-05-11 | 2021-11-23 | Ricoh Company, Ltd. | Device for fabricating three-dimensional fabrication object and method of manufacturing three-dimensional fabrication object |
US10730281B2 (en) | 2017-06-23 | 2020-08-04 | Hamilton Sundstrand Corporation | Method for additively manufacturing components |
-
2017
- 2017-06-23 US US15/631,814 patent/US10730281B2/en active Active
- 2017-10-17 US US15/785,695 patent/US20180370216A1/en not_active Abandoned
-
2018
- 2018-06-25 EP EP18179508.9A patent/EP3417963A1/en not_active Ceased
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014074947A2 (en) * | 2012-11-08 | 2014-05-15 | Das, Suman | Systems and methods for additive manufacturing and repair of metal components |
EP2865465A1 (en) * | 2013-09-27 | 2015-04-29 | Alstom Technology Ltd | Method for manufacturing a metallic component by additive laser manufacturing |
WO2016201309A1 (en) * | 2015-06-10 | 2016-12-15 | Ipg Photonics Corporation | Multiple beam additive manufacturing |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10730281B2 (en) | 2017-06-23 | 2020-08-04 | Hamilton Sundstrand Corporation | Method for additively manufacturing components |
EP3486005A1 (en) * | 2017-10-17 | 2019-05-22 | Hamilton Sundstrand Corporation | Method for additively manufacturing components |
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